Jet engine nacelle having a reverser flap

Abstract

A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

The invention claimed is: 
     
       1. A nacelle for a turbofan, the nacelle comprising:
 a fixed cowl having a front end and an aft end, and a movable cowl movable in translation in a translation direction between a closing position in which it is close to the fixed cowl and an opening position in which it is far aft of the fixed cowl, 
 an actuator configured to move the movable cowl from the closing position to the opening position, and vice versa, 
 a window delimited on an upstream side by the fixed cowl and on a downstream side by the movable cowl, the window being open between a duct for a bypass flow and the exterior of the nacelle, 
 a reverser flap mounted movable in rotation about a rotation axis between a closed position in which it obstructs the window and an open position in which it does not obstruct the window, and 
 a drive mechanism configured to coordinate the movement from the closed position to the open position of the reverser flap with the movement from the closing position to the opening position of the movable cowl and vice versa, the drive mechanism comprising:
 two bearings, each being mounted fixedly on a structure of the nacelle, 
 for each bearing, a lever arm, of which a first end is mounted movable in rotation on the bearing and of which a second end is mounted fixedly on the reverser flap, 
 for each lever arm, a rail integral with the movable cowl, each rail comprising a straight portion, of which an axis of the straight portion is parallel to the direction of translation of the movable cowl, and a curved portion that extends the straight portion towards the upstream side, 
 for each lever arm, a rod, of which a first end is mounted in an articulated manner on the lever arm, and 
 for each rail, a slider that is mounted so as to be movable in translation on the rail and is mounted so as to be articulated to a second end of the rod. 
 
 
     
     
       2. The nacelle according to  claim 1 , further comprising an additional flap mounted movable in rotation between a retracted position in which the additional flap is not positioned in the duct and an active position in which the additional flap is positioned across the duct and extends the reverser flap in the open position in the duct, and wherein the nacelle comprises additional means that coordinate the movement of the additional flap from the retracted position to the active position with the movement of the reverser flap from the closed position to the open position and vice versa. 
     
     
       3. The nacelle according to  claim 2 , wherein the additional means are in the form of a mechanical connection. 
     
     
       4. The nacelle according to  claim 3 , wherein the mechanical connection comprises an additional rod, of which a first end is mounted in an articulated manner on the additional flap, and of which the second end is mounted in an articulated manner on the reverser flap. 
     
     
       5. A turbofan comprising an engine and a nacelle according to  claim 1  surrounding the engine, and in which the duct for the bypass flow is delimited between the nacelle and the engine. 
     
     
       6. An aircraft comprising at least one turbofan according to  claim 5 .